超音速風洞の始動特性と流路形状の影響 Effects of Wind Tunnel Geometry on Starting Characteristics of a Supersonic Wind Tunnel

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抄録

To improve test capability at intermittent blow-down supersonic wind tunnels, diffuser performance is important to keep the starting pressure ratio as low as possible. A parametric study on the tunnel geometry for the JAXA 1m × 1m supersonic wind tunnel (JSWT) was conducted by numerical simulation. It was found that the diffuser part with a shock train has large effects on the starting pressure ratio. It was also indicated that oblique shock waves generated from the model support strut and the second throat ramp contributed the efficient pressure recovery. To improve the diffuser performance, we propose a design methodology considering these shock phenomena and designed a modified geometry for the JSWT. Although the cross-sectional area distribution was only changed from the original one, its higher performance was confirmed numerically. This design concept was also validated experimentally with a 10% scale model tunnel at a Mach number of 3.0.

収録刊行物

  • 日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences

    日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 59(691), 206-211, 2011-08-05

    一般社団法人 日本航空宇宙学会

参考文献:  14件中 1-14件 を表示

被引用文献:  1件中 1-1件 を表示

  • 超音速風洞の不始動予測

    赤塚 純一 , 西島 寛典 , 渡辺 光則 , 永井 伸治

    日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 60(5), 197-202, 2012-10-05

    J-STAGE 参考文献8件

各種コード

  • NII論文ID(NAID)
    10030274814
  • NII書誌ID(NCID)
    AA11307372
  • 本文言語コード
    ENG
  • 資料種別
    ART
  • ISSN
    13446460
  • NDL 記事登録ID
    11212350
  • NDL 雑誌分類
    ZN25(科学技術--運輸工学--航空機・ロケット)
  • NDL 請求記号
    Z74-B503
  • データ提供元
    CJP書誌  CJP引用  NDL  J-STAGE 
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